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Modulation of a ramp-induced shock wave/boundary layer interaction through extended frequency range pulsed discharge 认领 引用
1
作者 Hongyu WANG Hongxun LI +1 位作者 Gang WANG Tao LI 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2026年第5期216-234,共19页
Our experimental study explored the impact of pulse discharge energy deposition,across a wider frequencies ranging from 5 kHz to 20 kHz,on a Shock Wave/Boundary Layer Interaction(SWBLI)at a Mach number of 2.47.Using h... Our experimental study explored the impact of pulse discharge energy deposition,across a wider frequencies ranging from 5 kHz to 20 kHz,on a Shock Wave/Boundary Layer Interaction(SWBLI)at a Mach number of 2.47.Using high-speed schlieren imaging,Planar Laser Scattering(PLS)and Focused Laser Differential Interferometry(FLDI),we analyzed the characteristics of discharge-induced energetic eddies and their impact on SWBLI.The Spectral Proper Orthogonal Decomposition(SPOD)was employed to scrutinize the structural transformations of the flow field under the influence of pulse discharge.Our findings indicate that pulsed discharge significantly alters the flow field by propelling the separation shock upstream,with this effect intensifying as the discharge frequency increases.Additionally,the discharge diminishes the fluctuation intensity of the separation shock and the shear layer,and it reduces the low-frequency spectral energy of the separation shock.SPOD analysis revealed that at high discharge frequencies,the flow field dynamics shift from the low-frequency oscillations of the separation shock to the motion of vortices along the boundary layer,which interact with the shock waves.The control efficacy of pulsed discharge on SWBLI demonstrates remarkable consistency and intensity at frequencies of 10 kHz or higher,whereas a notable attenuation in effectiveness is observed at 5 kHz.This reveals a critical frequency threshold beyond which flow characteristics change markedly,primarily seen in the progressive weakening of the separation shock.However,further frequency increases beyond this point yield diminishing returns in SWBLI control effectiveness. 展开更多
关键词 Flow visualization Plasma flow control Shock wave/boundary layer interaction Supersonic flow Wind tunnel experiments
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Study of an adaptive bump control mechanism for shock wave/boundary layer interactions in supersonic flows 认领 引用 被引量：2
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作者 Shan-Shan Tian Liang Jin +2 位作者 Wei Huang Yang Shen Kai An 《Theoretical & Applied Mechanics Letters》 EI CAS CSCD 2025年第4期319-330,共12页
The stability of supersonic inlets faces challenges due to various changes in flight conditions,and flow control methods that address shock wave/boundary layer interactions under only one set of conditions cannot meet... The stability of supersonic inlets faces challenges due to various changes in flight conditions,and flow control methods that address shock wave/boundary layer interactions under only one set of conditions cannot meet developmental requirements.This paper proposes an adaptive bump control scheme and employs dynamic mesh technology for numerical simulation to investigate the unsteady control effects of adaptive bumps.The obtained results indicate that the use of moving bumps to control shock wave/boundary layer interactions is feasible.The adaptive control effects of five different bump speeds are evaluated.Within the range of bump speeds studied,the analysis of the flow field structure reveals the patterns of change in the separation zone area during the control process,as well as the relationship between the bump motion speed and the control effect on the separation zone.It is concluded that the moving bump endows the boundary layer with additional energy. 展开更多
关键词 Shock wave/boundary layer interaction Adaptive Flow control Bump Supersonic flow
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Rarefaction effect on non-equilibrium characteristics of laminar shock wave/boundary layer interaction 认领 引用 被引量：1
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作者 Jiahui SONG Long MIAO +4 位作者 Aiguo XU Yanbiao GAN Feng CHEN Yugan LIAO Xiao HOU 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2025年第10期311-326,共16页
A Discrete Boltzmann Method(DBM)with a Maxwell-type boundary condition is constructed to investigate the influence of rarefaction on laminar Shock Wave/Boundary Layer Interaction(SWBLI).Due to the complexity of compre... A Discrete Boltzmann Method(DBM)with a Maxwell-type boundary condition is constructed to investigate the influence of rarefaction on laminar Shock Wave/Boundary Layer Interaction(SWBLI).Due to the complexity of compressible flow,a Knudsen number vector Kn,whose components include the local Knudsen numbers such as Knρand KnU,is introduced to characterize the local structures,where Knρand KnUare Knudsen numbers defined in terms of the density and velocity interfaces,respectively.Since first focusing on the steady state of SWBLI,the DBM considers up to the second-order Knρ(rarefactionon-equilibrium)effects.The model is validated using Mach number 2 SWBLI and the necessity of using DBM with sufficient physical accuracy is confirmed by the shock collision problem.Key findings include the following:the leading-edge shock wave increases the local density Knudsen number Knρand eventually leads to the failure of linear constitutive relations in the Navier-Stokes(N-S)model and surely also in the lower-order DBM;the non-equilibrium effect differences in regions behind the leading-edge shock wave are primarily correlated with Knρ,while in the separation region are primarily correlated with KnU;the non-equilibrium quantities D2and D4,2,as well as the viscous entropy production rate SNOMFcan be used to identify the separation zone.The findings clarify various effects and main mechanisms in different regions associated with SWBLI,which are concealed in N-S model. 展开更多
关键词 Rarefaction effects Discrete Boltzmann method Shock wave/boundary layer interaction Thermodynamic non-equilibrium Kinetic theory
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Scaling analysis and experimental validation for incident shock wave/boundary layer interactions under the influence of gradual expansion waves 认领 引用
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作者 Yunjie GUO Ziyun WANG +5 位作者 Huijun TAN Yue ZHANG Yufeng HUANG Hongchao XUE Hang YU Hao ZHANG 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2025年第3期207-221,共15页
Cowl-induced incident Shock Wave/Boundary Layer Interactions (SWBLI) under the influence of gradual expansion waves are frequently observed in supersonic inlets. However, the analysis and prediction of interaction len... Cowl-induced incident Shock Wave/Boundary Layer Interactions (SWBLI) under the influence of gradual expansion waves are frequently observed in supersonic inlets. However, the analysis and prediction of interaction lengths have not been sufficiently investigated. First, this study presents a theoretical scaling analysis and validates it through wind tunnel experiments. It conducts detailed control volume analysis of mass conservation, considering the differences between inviscid and viscous cases. Then, three models for analysing interaction length under gradual expansion waves are derived. Related experiments using schlieren photography are conducted to validate the models in a Mach 2.73 flow. The interaction scales are captured at various relative distances between the shock impingement location and the expansion regions with wedge angles ranging from 12° to 15° and expansion angles of 9°, 12°, and 15°. Three trend lines are plotted based on different expansion angles to depict the relationship between normalised interaction length and normalised interaction strength metric. In addition, the relationship between the coefficients of the trend line and the expansion angles is introduced to predict the interaction length influenced by gradual expansion waves. Finally, the estimation of normalised interaction length is derived for various coefficients within a unified form. 展开更多
关键词 Supersonic flow Shock wave/boundary layer interactions Boundary layer separation Scaling analysis Prediction of interaction length
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Structural uncertainty quantification of Reynolds-Averaged Navier–Stokes closures for various shock-wave/boundary layer interaction flows 认领 引用 被引量：3
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作者 Fanzhi ZENG Tianxin ZHANG +2 位作者 Denggao TANG Jinping LI Chao YAN 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2024年第3期34-48,共15页
Accurate prediction of Shock-Wave/Boundary Layer Interaction(SWBLI)flows has been a persistent challenge for linear eddy viscosity models.A major limitation lies in the isotropic representation of the Reynolds stress,... Accurate prediction of Shock-Wave/Boundary Layer Interaction(SWBLI)flows has been a persistent challenge for linear eddy viscosity models.A major limitation lies in the isotropic representation of the Reynolds stress,as assumed under the Boussinesq approximation.Recent studies have shown promise in improving the prediction capability for incompressible separation flows by perturbing the Reynolds-stress anisotropy tensor.However,it remains uncertain whether this approach is effective for SWBLI flows,which involve compressibility and discontinuity.To address this issue,this study systematically quantifies the structural uncertainty of the anisotropy for oblique SWBLI flows.The eigenspace perturbation method is applied to perturb the anisotropy tensor predicted by the Menter Shear–Stress Transport(SST)model and reveal the impacts of anisotropy on the prediction of quantities of interest,such as separation and reattachment positions,wall static pressure,skin friction,and heat flux.The results demonstrate the potential and reveal the challenges of eigenspace perturbation in improving the SST model.Furthermore,a detailed analysis of turbulent characteristics is performed to identify the source of uncertainty.The findings indicate that eigenspace perturbation primarily affects turbulent shear stress,while the prediction error of the SST model is more related to turbulent kinetic energy. 展开更多
关键词 Shock-wave/boundary layer interaction(SWBLI) Turbulence models Uncertainty analysis Eigenspace perturbation Anisotropy
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Passage shock wave/boundary layer interaction control for transonic compressors using bumps 认领 引用 被引量：5
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作者 Yongzhen LIU Wei ZHAO +2 位作者 Qingjun ZHAO Qiang ZHOU Jianzhong XU 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2022年第2期82-97,共16页
Flow separation due to shock wave/boundary layer interaction is dominated in blade passage with supersonic relative incoming flow,which always accompanies aerodynamic performance penalties.A loss reduction method for ... Flow separation due to shock wave/boundary layer interaction is dominated in blade passage with supersonic relative incoming flow,which always accompanies aerodynamic performance penalties.A loss reduction method for smearing the passage shock foot via Shock Control Bump(SCB)located on transonic compressor rotor blade suction side is implemented to shrink the region of boundary layer separation.The curved windward section of SCB with constant adverse pressure gradient is constructed ahead of passage shock-impingement point at design rotor speed of Rotor 37 to get the improved model.Numerical investigations on both two models have been conducted employing Reynolds-Averaged Navier-Stokes(RANS)method to reveal flow physics of SCB.Comparisons and analyses on simulation results have also been carried out,showing that passage shock foot of baseline is replaced with a family of compression waves and a weaker shock foot for moderate adverse pressure gradient as well as suppression of boundary layer separations and secondary flow of low-momentum fluid within boundary layer.It is found that adiabatic efficiency and total pressure ratio of improved blade exceeds those of baseline at 95%-100%design rotor speed,and then slightly worsens with decrease of rotatory speed till both equal below 60%rated speed.The investigated conclusion implies a potential promise for future practical applications of SCB in both transonic and supersonic compressors. 展开更多
关键词 Flow separation Passage shock Shock Control Bump(SCB) Shock wave/boundary layer interaction Transonic compressors
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Passive shock wave/boundary layer control of wing at transonic speeds 认领 引用 被引量：1
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作者 Ling Zhou Dehua Chen +3 位作者 Yang Tao Guangyuan Liu Shuheng Song Shidong Zhong 《Theoretical & Applied Mechanics Letters》 CAS CSCD 2017年第6期325-330,共6页
At supercritical conditions a porous strip(or slot strip)placed beneath a shock wave can reduce the drag by a weaker lambda shock system,and increase the buffet boundary,even may increase the lift.Passive shock wave/b... At supercritical conditions a porous strip(or slot strip)placed beneath a shock wave can reduce the drag by a weaker lambda shock system,and increase the buffet boundary,even may increase the lift.Passive shock wave/boundary layer control(PSBC)for drag reduction was conducted by SC(2)-0714 supercritical wing,with emphases on parameter of porous/slot and bump,such as porous distribution,hole diameter,cavity depth,porous direction and so on.A sequential quadratic programming(SQP)optimization method coupled with ad]oint method was adopted to achieve the optimized shape and position of the bumps.Computational fluid dynamics(CFD),force test and oil test with half model all indicate that PSBC with porous,slot and bump generally reduce the drag by weaker lambda shock at supercritical conditions.According to wind tunnel test results for angle of attack of 2°at Mach number M=0.8,the porous configuration with 6.21%porosity results in a drag reduction of 0.0002 and lift-drag ratio increase of 0.2,the small bump configuration results in a drag reduction of 0.0007 and lift-drag ratio increase of 0.3.Bump normally reduce drag at design point with shock wave position being accurately computed.If bump diverges from the position of shock wave,drag will not be easily reduced. 展开更多
关键词 Wing Shock wave/boundary layer interactionl Bump Drag reductionl Transonic Optimization design
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Numerical evaluation of passive control of shock wave/boundary layer interaction on NACA0012 airfoil using jagged wall 认领 引用 被引量：3
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作者 Mojtaba Dehghan Manshadi Ramin Rabani 《Acta Mechanica Sinica》 SCIE EI CAS CSCD 2016年第5期792-804,共13页
Shock formation due to flow compressibility and its interaction with boundary layers has adverse effects on aerodynamic characteristics, such as drag increase and flow separation. The objective of this paper is to app... Shock formation due to flow compressibility and its interaction with boundary layers has adverse effects on aerodynamic characteristics, such as drag increase and flow separation. The objective of this paper is to appraise the practicability of weakening shock waves and, hence, reducing the wave drag in transonic flight regime using a two-dimensional jagged wall and thereby to gain an appropriate jagged wall shape for future empirical study. Different shapes of the jagged wall, including rectangular, circular, and triangular shapes, were employed. The numerical method was validated by experimental and numerical studies involving transonic flow over the NACA0012 airfoil, and the results presented here closely match previous experimental and numerical results. The impact of parameters, including shape and the length-to-spacing ratio of a jagged wall, was studied on aerodynamic forces and flow field. The results revealed that applying a jagged wall method on the upper surface of an airfoil changes the shock structure significantly and disintegrates it, which in turn leads to a decrease in wave drag. It was also found that the maximum drag coefficient decrease of around 17 % occurs with a triangular shape, while the maximum increase in aerodynamic efficiency（lift-to-drag ratio）of around 10 % happens with a rectangular shape at an angle of attack of 2.26？. 展开更多
关键词 Jagged wall Passive flow control Shock wave/boundary layer interaction Aerodynamic efficiency
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Direct numerical simulation of shock wave/boundary layer interaction controlled by steady microjet in a compression ramp 认领 引用 被引量：1
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作者 Ruoye XIAO Dong SUN Jian YU 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2024年第10期83-102,共20页
Shock wave/boundary layer interaction in a 24°turning angle of the compression ramp at Mach number 2.9 controlled by steady microjet is investigated using direct numerical simulation.Three different jet spacings ... Shock wave/boundary layer interaction in a 24°turning angle of the compression ramp at Mach number 2.9 controlled by steady microjet is investigated using direct numerical simulation.Three different jet spacings which are termed as sparse,moderate and dense are considered,and the induced vortex system and shock structures are compared.A moderate jet spacing configuration is found to generate counter-rotating vortex pairs that transport high-momentum fluid towards the vicinity of wall and strengthen the boundary layer to resist separation,reducing the separation region.The dense jet spacing configuration creates a larger momentum deficit region,reducing the friction downstream of the corner.Analysis of pressure and pressure gradient reveals that dense jet spacing configuration reduces the intensity of separation shock.The impact of varying jet spacings on the turbulent kinetic energy transport mechanism is also investigated by decomposing the budget terms in the transport equation.Furthermore,the spectral characteristics of the separation region are studied using power spectral density and dynamic mode decomposition methods,revealing that moderate jet spacing configuration suppresses low-frequency fluctuations in the separation region. 展开更多
关键词 Shock wave/boundary layer interaction Compression ramp Steady microjet Different jet spacings Direct numerical simulation
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Hypersonic Shock Wave/Boundary Layer Interactions by a Third-Order Optimized Symmetric WENO Scheme 认领 引用 被引量：1
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作者 Li Chen Guo Qilong +1 位作者 Li Qin Zhang Hanxin 《Transactions of Nanjing University of Aeronautics and Astronautics》 EI CSCD 2017年第5期524-534,共11页
A novel third-order optimized symmetric weighted essentially non-oscillatory(WENO-OS3)scheme is used to simulate the hypersonic shock wave/boundary layer interactions.Firstly,the scheme is presented with the achieveme... A novel third-order optimized symmetric weighted essentially non-oscillatory(WENO-OS3)scheme is used to simulate the hypersonic shock wave/boundary layer interactions.Firstly,the scheme is presented with the achievement of low dissipation in smooth region and robust shock-capturing capabilities in discontinuities.The Maxwell slip boundary conditions are employed to consider the rarefied effect near the surface.Secondly,several validating tests are given to show the good resolution of the WENO-OS3 scheme and the feasibility of the Maxwell slip boundary conditions.Finally,hypersonic flows around the hollow cylinder truncated flare(HCTF)and the25°/55°sharp double cone are studied.Discussions are made on the characteristics of the hypersonic shock wave/boundary layer interactions with and without the consideration of the slip effect.The results indicate that the scheme has a good capability in predicting heat transfer with a high resolution for describing fluid structures.With the slip boundary conditions,the separation region at the corner is smaller and the prediction is more accurate than that with no-slip boundary conditions. 展开更多
关键词 hypersonic flows shock wave/boundary layer interactions weighted essentially non-oscillatory(WENO)scheme slip boundary conditions
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A survey of panel aeroelasticity in shock-dominated flow:Perspectives from fluid-structure interactions and shock wave-boundary layer interactions 认领 引用 被引量：1
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作者 Aiming SHI Yiwen HE 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2026年第1期210-229,共20页
As a multidisciplinary phenomenon,panel aeroelasticity in shock-dominated flow is featured by two primary interactions:Fluid-Structure Interactions(FSIs)and Shock-Boundary Layer Interactions(SBLIs).The former raises s... As a multidisciplinary phenomenon,panel aeroelasticity in shock-dominated flow is featured by two primary interactions:Fluid-Structure Interactions(FSIs)and Shock-Boundary Layer Interactions(SBLIs).The former raises structural concerns,and the latter is of aerodynamic interest.Thus,panel aeroelasticity in shock-dominated flow represents a vital topic for the development and optimization of supersonic vehicles and propulsion systems.This review systematically summarizes recent advances in the methodologies applied to capture structural and fluid dynamics,including theoretical models,numerical simulations,and wind tunnel experiments.The application of data-driven modal decomposition,an advanced technique to extract physically crucial features,on the topic is introduced.From the perspective of FSIs,the distinctive aeroelastic behaviors in shock-dominated flow,including hysteresis phenomena and nonlinear responses,are highlighted.From the perspective of SBLIs,the modifications in their spatial and temporal characteristics imposed by the aeroelastic responses are emphasized.Motivated by the interaction between the shock waves and structural response,different strategies have been proposed to implement aeroelastic suppression and shock control,which have the potential to enhance structural safety and aerodynamic performance in the next generation of high-speed flight vehicles. 展开更多
关键词 Aeroelasticity Fluid structure interaction Modal decomposition Shock boundary layer interactions Shock waves
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Coupling of 0D/1D Grain Boundaries Inducing Extreme Charge Rearrangement/Magnetic Resonance for Ultrabroadband Electromagnetic Wave Absorption 认领 引用
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作者 Jie Huang Liuying Wang +7 位作者 Renbing Wu Weichao Wang Chaoqun Ge Haoke Yang Xu Tang Wenyu Jiao Gu Liu Bin Wang 《Carbon Energy》 SCIE EI CAS CSCD 2026年第3期201-212,共12页
Ferrite-carbon composites effectively absorb electromagnetic(EM)waves via coupled mechanisms.However,the dynamic evolution of intrinsic polarization and magnetic loss mechanisms following interfacial coupling has long... Ferrite-carbon composites effectively absorb electromagnetic(EM)waves via coupled mechanisms.However,the dynamic evolution of intrinsic polarization and magnetic loss mechanisms following interfacial coupling has long been overlooked,impeding broadening of the ultra-broadband EM wave absorption performance in heterostructures.Herein,via surface ligand modulation,in situ growth of 0D Fe3O4quantum dots(QDs)on the surface of 1D carbon nanotubes triggers grain boundary coupling.The energy rebalancing effect at the interface induces an extreme charge rearrangement within the Fe3O4QDs.This rearrangement enhances dipole orientation hysteresis and charge accumulation,resulting in charge and interfacial polarization losses.Meanwhile,for subcritical Fe3O4QDs,short-range magnetic resonance and magnetic exchange-triggered magnetic resonance transfer synergistically enhance the magnetic loss.Through charge rearrangement/magnetic resonance induced by0D/1D grain boundary coupling,an effective bandwidth of nearly 10 GHz is achieved at a minimal thickness of 2 mm,covering the X and Ku bands.This strategy provides an effective paradigm and novel theoretical insights for ultra-broadband electromagnetic wave absorption applications. 展开更多
关键词 charge rearrangement electromagnetic wave absorption ferrite–carbon matrix composites grain boundary coupling
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GLOBAL EXISTENCE AND ASYMPTOTIC BEHAVIOR FOR INITIAL-BOUNDARY VALUE PROBLEMS OF ONE-DIMENSION QUASILINEAR WAVE EQUATIONS WITH NULL CONDITIONS 认领 引用
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作者 Dongbing ZHA Yitong SUN Tingqiang HOU 《Acta Mathematica Scientia》 SCIE CSCD 2026年第2期568-594,共27页
We consider the initial-boundary value problems on R+×R+ for one-dimension systems of quasilinear wave equations with null conditions.We first show that for homogeneous Dirichlet boundary values and suffici... We consider the initial-boundary value problems on R+×R+ for one-dimension systems of quasilinear wave equations with null conditions.We first show that for homogeneous Dirichlet boundary values and sufficiently small initial data,classical solutions always globally exist.Then we prove that the global solution will scatter,i.e.,it will converge to some solution of one dimensional homogeneous linear wave equations as time tends to infinity,in the energy sense.Finally we show the inverse scattering result:the scattering data can determine the global solution uniquely. 展开更多
关键词 one-dimension quasilinear wave equations null condition global existence scattering inverse scattering
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An analytical study for detonation wave boundary layer interactions under reflections 认领 引用
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作者 Hao YAN Xin HAN +2 位作者 Haochen XIONG Chongguang SHI Yancheng YOU 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2026年第2期178-201,共24页
Numerical simulations and theoretical models are developed in this paper for the Detonation-Wave/Boundary-Layer Interactions(DWBLIs)under reflections.Transient flow fields demonstrate the highly non-stationarity of th... Numerical simulations and theoretical models are developed in this paper for the Detonation-Wave/Boundary-Layer Interactions(DWBLIs)under reflections.Transient flow fields demonstrate the highly non-stationarity of the DWBLIs when Mach Reflection(MR)occur,and subsequent analyses show that the subsonic region introduced by the boundary layer exacerbates the instability.Further quantitative analyses show that viscosity has little effect on propulsive performance and the separation wave can be considered as an oblique detonation wave.Influence parameters to DWBLIs such as combustion chamber height,incoming Mach number,equivalence ratio,and inlet channel length are categorized and studied.Besides simulations,theoretical analytical modeling is established for Regular Reflection(RR)and MR of DWBLIs.Multiple formulas for the separation zone length are obtained according to the mass conservation under different transformation type between inviscid and viscid reflections.Comparison with the numerical simulations verifies the validity of the model and it can be further generalized to the curved DWBLIs.The developed model makes the theoretical solution process of DWBLIs possible and provides the key foundation for further analysis and solution. 展开更多
关键词 Boundary layer interaction Detonation wave Hypersonic flow Reflection Viscosity
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Three-dimensional curved conical shock wave/plate boundary layer interactions 认领 引用
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作者 Jianrui CHENG Tao ZHANG +3 位作者 Zhenqi SUN Chongguang SHI Chengxiang ZHU Yancheng YOU 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2025年第12期32-45,共14页
Three-dimensional curved shock wave/boundary layer interaction with streamwise and spanwise curvatures widely exists in practical aerodynamic design.To explore the effects of composite shock curvatures on boundary lay... Three-dimensional curved shock wave/boundary layer interaction with streamwise and spanwise curvatures widely exists in practical aerodynamic design.To explore the effects of composite shock curvatures on boundary layer separation,a canonical model with a cone placed above plate was utilized as a reference.Configurations of straight,convex,and concave conical shock waves inducing the curved conical shock wave/boundary layer interactions were studied,using CFD based on Reynolds-averaged numerical simulation method.The flow structure and separation region of each case were discussed quantitively on the symmetry plane,flat plate,and plane perpendicular to flow direction,respectively.The focus of the analysis was on the characteristic patterns of separation scale variation in the streamwise and spanwise directions,which were observed to consistently change with respect to both directions with alterations in the incident shock wave shape.A simplified control volume model was established to qualitatively discuss the influence source of curved shock waves on separation scales,based on mass conservation equations.The results suggest that the curved shock wave has a holistic effect on separation,which is not solely dependent on the shock foot strength. 展开更多
关键词 Flow separation Reynolds-averaged Shock waves Shock wave/boundary layer interaction Three-dimensional flow
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Formation and solute segregation for an asymmetric tilt boundary on{1012}twin boundaries 认领 引用 被引量：6
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作者 Qiang Yang Shuhui Lv +3 位作者 Peng Chen Zefeng Xie Shuo Zhou Xin Qiu 《Journal of Magnesium and Alloys》 SCIE EI CAS CSCD 2025年第2期583-591,共9页
Asymmetric tilt boundaries on conventional twin boundaries(TBs)are significant for understanding the role of twins on coordinating plastic deformation in many metallic alloys.However,the formation modes of many asymme... Asymmetric tilt boundaries on conventional twin boundaries(TBs)are significant for understanding the role of twins on coordinating plastic deformation in many metallic alloys.However,the formation modes of many asymmetric tilt boundaries are hard to be accounted for based on traditional theoretical models,and the corresponding solute segregation is complex.Herein,atomic structures of a specific asymmetric boundary on{1012}TBs were reveled using aberration-corrected high-angle annular dark-field scanning transmission electron microscopy(HAADF-STEM),molecular dynamics(MD)and density functional theory(DFT)simulations.Reaction betweenM dislocations and the{1012}TB can generate a~61°/25°asymmetric tilt boundary.The segregation of Gd and Zn atoms is closely related to the aggregateddislocations and the interfacial interstices of the asymmetric tilt boundary,which is energetically favorable in reducing the total system energy. 展开更多
关键词 Magnesium alloy Transmission electron microscopy Twin boundary Dislocation Segregation
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Receptivity of a hypersonic blunt cone boundary layer to freestream entropy and vorticity waves 认领 引用 被引量：1
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作者 Menghao Niu Caihong Su 《Acta Mechanica Sinica》 SCIE EI CAS CSCD 2025年第6期93-104,共12页
Hypersonic boundary-layer receptivity to freestream entropy and vorticity waves is investigated using direct numerical simula-tions for a Mach 6 flow over a 5.08 mm nose radius cone.Two frequencies of 33 kHz and 150 k... Hypersonic boundary-layer receptivity to freestream entropy and vorticity waves is investigated using direct numerical simula-tions for a Mach 6 flow over a 5.08 mm nose radius cone.Two frequencies of 33 kHz and 150 kHz are considered to be rep-resentative of the first and second instability modes,respectively.For the first mode,wall pressure fluctuations for both entropy and vorticity wave cases exhibit a strong modulation yet without a growing trend,indicating that the first mode is not generated despite its instability predicted by linear stability theory.The potential reason for this is the absence of postshock slow acoustic waves capable of synchronizing with the first mode.By contrast,for the second mode,a typical three-stage boundary-layer response is observed,consistent with that to slow acoustic waves studied previously.Furthermore,the postshock disturbances outside the boundary layer can be decomposed into the entropy(densityemperature fluctuations)and vorticity components(ve-locity fluctuations),and the latter is shown to play a leading role in generating the second mode,even for the case with entropy waves where the densityemperature fluctuations dominate the postshock regions. 展开更多
关键词 Hypersonic Boundary layer Receptivity Entropy wave Vorticity wave
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High-amplitude wall heat flux events in an impinging shock wave/turbulent boundary layer interaction 认领 引用
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作者 Xianxu YUAN Fulin TONG +2 位作者 Junjie LIMEI Xiangxin JI Xinliang LI 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2025年第6期336-348,共13页
This study focuses on High-Amplitude Wall Heat Flux events(HAWHFs) occurring during the interaction between a supersonic flat-plate Turbulent Boundary Layer(TBL) at a Mach number of2.25 and an oblique shock wave impin... This study focuses on High-Amplitude Wall Heat Flux events(HAWHFs) occurring during the interaction between a supersonic flat-plate Turbulent Boundary Layer(TBL) at a Mach number of2.25 and an oblique shock wave impinging at 33.2.. A database from a validated direct numerical simulation is analyzed using conditional averaging and a two-dimensional clustering methodology to elucidate the statistical characteristics of both positive and negative HAWHFs within the interaction region. The results reveal that the interaction considerably affects the temporal attributes of the HAWHFs, leading to an extended lifespan for the positive HAWHFs and an increased interval between the occurrences of negative HAWHFs. The structural characteristics of the identified HAWHFs are delineated based on the evolution of population density, aspect ratio, and both absolute and relative distances throughout the interaction. The joint probability density functions of the relative positioning of two adjacent structures indicate that, away from the reattachment point, the positive HAWHFs align in the spanwise direction, displaying similarities with the negative HAWHFs. Moreover, a conditional analysis of flow structures associated with HAWHFs is conducted. This analysis of the conditionally averaged three-dimensional fields reveals that the interaction fosters larger-scale organizational patterns in the downstream region. However, the formation of positive and negative HAWHFs remains largely unaffected by the interaction, with the former predominantly linked to a two-layer temperature structure and the latter primarily associated with a pair of oblique vortices. 展开更多
关键词 Shock wave Turbulent boundary layer Wall heat flux Extremeevents Direct numerical simulation
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Achieving serrated grain boundaries within gradient microstructures of nickel-based superalloys for dual-property turbine disks in aeroengines 认领 引用 被引量：1
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作者 Bingchao XIE Yongquan NING +4 位作者 Youwei LUO Zhaotian WANG Bowen SHI Mei ZHAN Mingwang FU 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2026年第2期641-660,共20页
Gradient microstructures strengthened by serrated Grain Boundaries(GBs)were achieved through a combination of Gradient Strain Deformation(GSD)and Serration Heat Treatment(SHT),with particular focus on microstructural ... Gradient microstructures strengthened by serrated Grain Boundaries(GBs)were achieved through a combination of Gradient Strain Deformation(GSD)and Serration Heat Treatment(SHT),with particular focus on microstructural evolution,underlying mechanisms,and the critical influencing factors.Dynamic recrystallization governed the microstructural evolution in the fine-grained and transition regions during GSD,where multiple nucleation mechanisms were active.Plastic deformation facilitated the dissolution ofγ'phase in fine-grained regions,ultimately resulting in its morphological transformation.During the subsequent SHT,serrated GBs formed within the gradient microstructures produced by prior GSD without disrupting the grain size gradient,thereby enhancing creep resistance.Two distinct mechanisms associated withγ'gbparticles governed the formation of the serrations at GBs.Owing to the stronger dragging effect of grain boundary junctions in fine-grained regions,the amplitude and wavelength of serrations in these regions were smaller than those in coarse-grained regions.Moreover,the formation of serrations exhibited a strong dependence on the inherent properties of the GBs.The random high-angle grain boundaries(HAGBs)with misorientation angles in the range of 30-59°tended to become serrated more easily during SHT due to their high mobility and the accelerated precipitation ofγ'gbparticles at them.Low-ΣHAGBs and low-angle GBs were not prone to form serrations.In particular,serration formation was completely inhibited atΣ3 twin boundaries due to their extremely low mobility and the absence ofγ'gbparticles. 展开更多
关键词 Gradient microstructures Grain boundary migration Grain boundary properties Serrated grain boundaries Serration formation mechanisms Superalloys
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In Situ MOF Pyrolysis Construction of Hierarchical Porous Co-Nanoparticles/Carbon Cloth Composites for Enhanced Electromagnetic Wave Shielding and Absorption 认领 引用 被引量：1
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作者 Changlong Du Lei Yu +7 位作者 Jieping Wang Sichun Xiong Pengpeng Mou Lianrui Li Zhi Nie Gengping Wan Jianguo Wen Guizhen Wang 《Rare Metals》 SCIE EI CAS CSCD 2026年第2期515-526,共12页
The development of high-performance electromagnetic protection materials integrating broadband absorption and effective shielding capabilities is hindered by challenges in simultaneously optimizing multiple electromag... The development of high-performance electromagnetic protection materials integrating broadband absorption and effective shielding capabilities is hindered by challenges in simultaneously optimizing multiple electromagnetic properties through conventional material designs.This study pioneers a hierarchical porous Co nanoparticle/carbon cloth(Co/CC)composite via controlled annealing of a Co-MOF precursor on carbon cloth.The Co-MOF served a dual role as both magnetic source and poreforming agent,enabling in situ generation of uniformly dispersed Co nanoparticles and creation of abundant pores/interfaces on the CC fibers during pyrolysis.This unique architecture synergistically enhanced dielectric loss(via interfacial/dipolar polarization)and magnetic loss(via natural resonance,exchange interactions,and eddy currents),significantly improving impedance matching.The hierarchical pores further functioned as integrated“absorption-reflection”units for efficient electromagnetic energy attenuation.Consequently,the Co/CC composite annealed at 800℃(Co/CC-800)achieves minimum reflection loss(-40.69 dB)and 120%effective absorption bandwidth extension(6.16 GHz)as a filler,and exhibits superior electromagnetic interference shielding effectiveness(46.66 dB)as an integrated component.Significantly,Co/CC-800 demonstrated robust photothermal and electrothermal conversion capabilities,ensuring operational stability in ice-covered and humid harsh environments.This work pioneers a pore-structure-mediated strategy to harmonize dielectric-magnetic synergy,providing a new paradigm for designing advanced multifunctional electromagnetic protection materials. 展开更多
关键词 dielectric-magnetic synergy electromagnetic wave absorption electromagnetic wave shielding structural regulation
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